航天器环境工程2017，Vol.34Issue(4)：343-349,7.DOI:10.3969/j.issn.1673-1379.2017.04.001
微泵驱动流体回路主动热控系统在轨测试试验研究
The flight experiments of active thermal control system with micro-mechanical pumped fluid loop
摘要
Abstract
This paper reviews the design scheme and the ground test results of the launched fluid loop system, focusing on the flight experiment scheme and the corresponding results. The flight experiment of the developed fluid loop system includes the open-loop test, the closed-loop test and the on-orbit long life test of two micro-mechanical pumps. The experiment results indicate that all components of the developed fluid loop system can meet the requirements of the space environment; the hardware and software performance of the system is long-time stable on the orbit; the micro-mechanical pumped fluid loop system has a flexible thermal management capacity, in that it achieves a rapid heat collection and heat transfer for the spacecraft.关键词
主动热控/微泵/流体回路/在轨测试试验Key words
active thermal control/micro-mechanical pump/fluid loop/in-flight measurement test分类
航空航天引用本文复制引用
曹建光,顾燕萍,陈钢,孙伟伟,王江,刘冈云..微泵驱动流体回路主动热控系统在轨测试试验研究[J].航天器环境工程,2017,34(4):343-349,7.基金项目
国家863重大专项课题(编号:2013AA8073034) （编号:2013AA8073034）
上海市科研技术项目(编号:14QB1404200) （编号:14QB1404200）
